Missile launcher



Nov. 21, 1961 R. A. LYNCH MISSILE LAUNCHER Filed Dec. 2, 1958 VENT ROBER LYN ATTQRNEY United States i atent 3,009,393 MISSILE LAUNCHER Robert A. Lynch, San Diego, Calif., assignor to General Dynamics Corporation, San Diego, Calif., a corporation of Delaware Filed Dec. 2, 1958, Ser. No. 777,752 3 Claims. (Cl. 89-1.7)

The present invention relates to a missile launcher, and more particularly relates to a launcher which provides the initial spin for stabilizing rockets or missiles after they have left the launcher.

Prior launchers which have provided missiles with an initial spin have done so by using exterior gas driven or mechanically driven motors to rotate the missile launch tube while the missile is being launched therefrom. These exterior power sources unduly burden a launcher because of their weight and bulk. This is particularly true where the launcher is to be portable so that it may be utilized by mobile ground forces or the like.

The present invention, however, is not subject to these disadvantages because it utilizes the exhaust gases of the missile itself, coupled with a unique and novel launching apparatus, to produce the initial spin of the missile as it is launched from the launcher.

Therefore, an object of the present invention is to pro vide a missile launcher which spins a missile as it is launched therefrom, which spin is produced without the use of any exterior power source.

Another object of the present invention is to provide a missile launcher which utilizes the energy of the missiles exhaust gases to produce the initial spin of the missile.

Another object is to provide an extremely light weight and mobile missile launcher which is particularly adapted for use by ground troops.

Other objects and features of the present invention will be readily apparent to those skilled in the art from the following specification and appended drawing wherein is illustrated a preferred form of the invention, and in which:

FIGURE 1 is a side elevational view of the missile launcher with portions thereof broken away to help clarify some of its constructional features.

FIGURE 2 is a. cross sectional view taken along line H--II of FIGURE 1.

FIGURE 3 is a rear end view of the missile launcher.

Referring now to the drawing, the missile launcher is shown therein as being composed of a launch tube 10 and a support tube 11 which is concentrically disposed about a portion of the length of the launch tube. Structurally rigid rings 12 are firmly fixed to the exterior of launch tube 10 to give it increased structural rigidity. Ring members 12 have a substantially L-shaped cross section which helps them resist distortion. The launch tube 10 is so formed that it has four grooves 13 disposed therein parallel to the cylindrical axis of the launch tube. The grooves 13 run almost the entire length of launch ube .10.

The rear end portion of the launch tube, which portion is indicated by arrow 14, includes a fan blade section or stator section 16. Stator section 16 has a substantially cylindrical cross section and has a plurality of blades or airfoils 17 attached to its interior circumference. The stator blades 17 form a concentric ring within the launch tube. The blades are can-ted so that they are disposed at some angle with respect to the cylindrical axis of the launch tube 10. A concentric ring or hub 18 is connected to the stator blades 17 to give them structural rigidity when subjected to missile exhaust blast. It should be noted that the stator blades 17 do not entirely fill the launch tube but leave a central open area.

Two annular flanges 19 are attached to the exterior "ice circumference of the launch tube. One such flange 19 is shown in the broken out section of FIGURE 1 While the other is hidden by support tube 11. The outer circumferences of flanges 19 contain grooves or annular tracks '20. These flanges with their annular tracks are the connecting structure between launch tube 10 and the outer support tube 11.

Support tube 11 has a pair of dual flanges 25 disposed at each end thereof which form parallel circumferential rings about support tube 11. A plurality of bearings 23 are disposed between dual flanges !25 and protrude through openings 31 in the support tube to ride in the annular tracks 20 of the launch tube. The launch tube is thus rotatively supported within the outer support tube and relative longitudinal movement is prohibited by the track and bearing arrangement. The bearings used to accornplish this are conventional roller type bearings set in lightweight cast housings 30 on axes or hearing shafts 24. The housings are fixed between dual flanges 25, and cover strips 27 are fixed to the flanges to complete the bearing cover. A seal 26 is used on each end of the support tube to prevent dirt and other debris from entering the bearings and annular tracks. The dirt seals 26 are attached to the flanges 25 on the ends of the support tube, and protrude inwardly to lie in contiguous relationship with respect to flanges 19 of the launch tube.

Since the support tube 11 must rotatively support the launch tube and a missile therein, it has a number of annular grooves or protrusions 28 to increase its structural rigidity. The lightweight yet rigid construction of the missile launcher makes it ideally suited for uses where mobility is a prime requisite. The unique features of the present invention, however, are also directed at producing an initial missile spin without the use or need for any bulky and heavy exterior power sources. An explanation of the functioning of the launcher should clearly show how this is achieved.

The missile launching sequence, or operation, begins with a missile disposed in launch tube 10 as shown in FIGURE 1 by dashed outline 29. Missile 29 has fins 32 which fit into grooves 13 of launch tube 10. The fit between the fins 32 and the grooves 13 is such that frictional forces are produced when the fins 32 attempt to move along the grooves 13.

With the missile fully inserted in the launch tube, as shown in FIGURE 1, then the missiles rocket motor can be ignited. This is conventionally accomplished by means of a small charge or squib on the end of an electrical cable. An electrical cable is shown in FIGURE 1, and is designated by numeral 33. Electrical current applied to cable 33 causes the igniter squib or charge to ignite the rocket. The initial blast of the rocket motor spews the electrical cable 33 and the ignition apparatus out through the central opening in the concentric ring of fan blades 17. The missile 29 then starts to move out of launch tube 10. At the same time, however, the exhaust blast from the rocket engine strikes the canted fan blades which are disposed in the rear end or exhaust end portion 14 of the launch tube. The effect of this exhaust blast on the canted fan blades is twofold. 'First, the canted fan blades and attached launch tube '10 are forced to rotate and the missile held within the tube is thus forced to rotate also. The amount of rotation or the rate thereof which is caused by the exhaust blast is substantially prescribed by the angle which the fan blades make with the cylindrical axis of the launch tube. The second efiect of the exhaust blast on the fan blades is to produce a recoil -which is directed rearwardly along the cylindrical axis of the launch tube. This recoil is also substantially controlled by the angle of the fan blades.

While the exhaust blast is thus rotating the launch tube and attempting to force the fan blades and attached launch 3 tube in a rearward direction, an opposing force is also being produced to counteract this rearward recoil effect. This opposing force, or forces, is created by the missile fins 32 as they attempt to move along grooves 13 of the launch tube. The friction between a fin and its associated groove produces a force which is substantially parallel to the cylindrical axis of the launch tube and which is directed toward the forward or exit end of the launch tube summation of the forces associated with all of the fin and groove arrangements is, similarly, a force parallel to the cylindrical axis of the launch tube and directed in the forward direction. This forward force opposes and substantially ofisets or counteracts the axial recoil force on the fan blades in the exhaust portion of the launch tube. Thus, the launching of a missile creates no appreciable recoil forces on the launcher so that its lightweight is no disadvantage during firing operations. And, the missile is given an initial stabilizing spin without the use of exterior power sources.

During actual field firings the outer or support tube 11 can be held at an elevated angle much like a mortar if so desired. The structure or mechanism for accomplishing this is not shown in the drawing however, as it felt that it is not an essential portion of the present invention nor is it necessary for an understanding thereof.

While certain preferred embodiments of the invention have been specifically disclosed, it is understood that the invention is not limited thereto as many variations will be readily apparent to those skilled in the art and the in vention is to be given its broadest possible interpretation within the terms of the following claims.

What I claim is:

1. A missile launcher comprising a substantially cylindrical launch tube, a support tube concentrically disposed about a portion of the length of said launch tube, said support tube having a first end and a second end, a plurality of bearings disposed at each of said ends, said bearings rotatively supporting said launch tube in said support tube, said bearings being fastened to said support tube, said launch tube having two annular tracks in which said bearings are positioned, said bearings and tracks preventing relative longitudinal movement between said launch tube and said support tube, said launch tube having an open exit end, an open exhaust end, a substantially cylindrical interior wall surface, a plurality of grooves in said interior wall surface disposed parallel to the cylindrical axis of said launch tube, each of said grooves having an open end and a closed end, said closed groove ends lying substantially adjacent said exhaust end and said open groove ends lying in said open exit end, each of said grooves being arranged to receive protrusions of a missile disposed within said launch tube and cooperating therewith to produce frictional drag forces parallel to said cylindrical axis upon movement of said missile protrusions within said launch tube, a plurality of airfoil impeller blades radially disposed about the interior of the exhaust end of said launch tube, a ring member concentrically positioned within said launch tube and attached to said impeller" blades, said ring member being open to pass portions of said exhaust gas theretlu'ough, said blades being canted at an angle with respect to said cylindrical axis to convert a portion of the launch tube exhaust gas forces into an axial recoil force and a rotation producing torque to rotate said launch tube, said opening in said ring member being of a size that said axial recoil force is of a magnitude to substantially balance said frictional drag forces.

2. A missile launcher comprising a support structure, a su s ntially y n ica launch t be s pp te y said The.

support structure to be rotated about its cylindrical axis, said launch tube having an open exit end, an open exhaust end, a. substantial cylindrical interior wall surface, a plurality of grooves in said interior wall surface, said grooves disposed parallel to the cylindrical axisof said launch tube and each having an open end and a closed end, said closed grooved ends lying substantially adjacent to said exhaust end, said open groove ends lying in said launch tube open exit end, said grooves arranged to receive protrusions of a missile disposed in said launch tube and cooperating therewith to produce frictional drag forces parallel to said cylindrical axis upon movement of said missile protrusion within said launch tube,.a concentric ring'positioned within said open exhaust end, a plurality of spaced airfoils radially attached between said ring and said launch tube, missile exhaust gases being capable of passing between said airfoils andpassing through the open space of said ring out of said open exhaust end, said airfoils being canted to partially convert launch tube exhaust gas forces into rotation producing torque on said launch tube, said airfoils and said ring partially obstructing launch tube exhaust flow creating an axial recoil force simultaneous with and opposed to said frictional forces, the contact area that said airfoils and said ring present to said exhaust flow being sufiicient to create a magnitude of recoil force that substantially balances said frictional drag forces.

3. A missile launcher for launching missiles with outwardly protruding members which missiles utilize high velocity exhaust forces for propulsion comprising, a support tube, a substantially cylindrical launch tube rotatably supported within said support tube, said launch tube having an open exit end and an open exhaust end and being rotatable about its cylindrical axis, said launch tube hav ing an interior wall surface, said wall surface having groove means disposed parallel to the axis of said launch tube for receiving the protrubing missile members and for providing frictionalresistance to movement 'of the missile longitudinally to said launch tube, said frictional resistance producing a force on said launching tube in a direction toward said open exit end when said missile is launched, air foil means being canted and partially obst-ructing launch tube exhaust flow for simultaneously converting launch tube exhaust gas forces into rotation producing torques on said launch tube and for producing a force on said launch tube in opposition to said force created by said frictional resistance when the missile is launched, said airfoil means being attached to said launch tube adjacent said exhaust end and projecting a distance radially inwardly from said tube to an extent that an opening is formed in said exhaust end through which portions of said exhaust passes, said opening being of a size that said force on said launch tube created by said exhaust is of a magnitude to balance said force produced by said frictional resistance.

References Cited in the file of this patent UNITED STATES PATENTS 2,701,984 Terce Feb. 15, 1955 2,775,163 Vegren Dec. 26, 1956 2,835,170 Kindelberger May 20, 1958 2,871,762 Schmued Feb. 3, -9

FOREIGN PATENTS 89,970 Sweden Aug. 10, 1937 912,398 France Apr. 29, 1946 4.57.201 It y y 5a 

